EP3009610A1 - Steam turbine gland seal arrangement - Google Patents

Steam turbine gland seal arrangement Download PDF

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Publication number
EP3009610A1
EP3009610A1 EP14290311.1A EP14290311A EP3009610A1 EP 3009610 A1 EP3009610 A1 EP 3009610A1 EP 14290311 A EP14290311 A EP 14290311A EP 3009610 A1 EP3009610 A1 EP 3009610A1
Authority
EP
European Patent Office
Prior art keywords
turbine
gland
steam
seal arrangement
steam turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP14290311.1A
Other languages
German (de)
French (fr)
Other versions
EP3009610B1 (en
Inventor
Frédéric Santais
Laurent Asset
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
GE Vernova GmbH
Original Assignee
Alstom Technology AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP14290311.1A priority Critical patent/EP3009610B1/en
Priority to RU2015142774A priority patent/RU2679953C2/en
Priority to US14/876,857 priority patent/US9915160B2/en
Priority to CN201510659945.9A priority patent/CN105507956B/en
Publication of EP3009610A1 publication Critical patent/EP3009610A1/en
Application granted granted Critical
Publication of EP3009610B1 publication Critical patent/EP3009610B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K23/00—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids
    • F01K23/02—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled
    • F01K23/06—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K23/00—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids
    • F01K23/02—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled
    • F01K23/06—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
    • F01K23/10—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/28—Arrangement of seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/15—Heat shield
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/60—Shafts
    • F05D2240/63—Glands for admission or removal of fluids from shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/171—Steel alloys

Definitions

  • the present disclosure relates generally to steam turbines and more particularly to multi pressure steam turbine gland arrangements of a labyrinth type for reducing steam leakage between rotating and stationary components of a steam turbine.
  • a gland sealing system In a steam turbine, the leakage of the turbine driving steam to the outside is typically prevented by a gland sealing system.
  • the system typically comprises a series of at least three labyrinth packing segments located along the turbine rotor in the region where the rotor exits the turbine casing.
  • a gland carrier casing supporting the sealing rings may form at least two chambers with the turbine casing The chamber(s) enables the ejection of a mixture of steam- air and an injection of steam, when there is more than one chamber in the upstream higher pressure chamber.
  • Each of these chambers are separated by sealing rings or labyrinth packing segments.
  • system with not less than two chambers may, for example, comprise a first chamber in which a mixture of steam/air is injected and a second chamber with in which steam is either injected or ejected depending on the operating mode.
  • the first chamber could operate at a pressure about 0.95 bar while the second chamber could operate at a pressure about 1.15 bar.
  • each of the packing segments is mounted on a gland carrier casing of the turbine.
  • the gland carrier casing component on which the sealing rings are mounted additionally forms part of the steam turbine exhaust
  • the turbine casing component may be exposed to local gland chambers temperature as well as steam turbine exhaust temperature.
  • the temperature gradient may be 110°C on the high pressure side and 70 °C on the intermediate pressure side. This may result in the turbine casing component being exposed to large thermal stresses.
  • a steam turbine gland seal arrangement is disclosed that can provide a means of reducing thermal stresses in turbine casing components on which seal segments are mounted thereby improving, for example, the tightness of the typical horizontal joint plane at which upper and lower parts of a typical steam turbine casing are jointed together by reducing thermal stresses in the extremity of the casing due to steam temperature differences between the turbine exhaust and the gland exhaust chamber.
  • the disclosure is based on the general idea of providing a heat shield in chambers formed between and by gland carrier and a turbine casing component.
  • the heat shields are arranged such that direct contact of the turbine casing component and steam flow in the chambers is avoided. In this way, a space between thermal shields and inner surface of the casing is created. This spaces acts as insulation thus avoiding a local cooling of the horizontal upper and lower half jointing flange, thus reducing joint distortion which in turn has the possible effect of improving joint tightness,
  • An aspect provides a steam turbine gland seal arrangement for preventing leakage of steam from around a turbine rotor.
  • the gland seal arrangement comprises a turbine casing component configured to be a portion of a steam turbine exhaust, a gland carrier and a plurality of sealing segment adjacently mounted in series on the gland carrier in a turbine axial direction, for sealing along a turbine axial direction of the rotor.
  • the casing component and the gland carrier are configured and arranged such that at least two chambers are formed, wherein the chamber includes a heat shield extending to partition the chamber.
  • the heat shield is bolted to the gland carrier.
  • the heat shield is made of stainless steel.
  • FIG. 1 An exemplary steam turbine gland seal arrangement shown in Fig. 1 is mounted around a turbine rotor 10.
  • the gland seal arrangement includes a turbine casing component 14, a gland carrier 12 mounted on the turbine casing component 14, a chamber formed by the turbine casing component 14, the gland carrier 12, and a heat shield 16 formed between the turbine casing component 14 and the gland carrier 12.
  • the turbine casing component 14 may be configured as a portion of a steam turbine exhaust 22. That is, the turbine casing component 14 may be configured to be partially located in a flow path region of the steam turbine downstream of turbine blades where steam is expanded. While in one exemplary embodiment, the turbine casing component 14 is made of a single piece, in another exemplary embodiment, the turbine casing component 14 is made of several pieces that are bonded, joined or welded in a way that enables thermal conduction through the turbine casing component 14.
  • a gland carrier 12 is a sealing carrying member whose purpose is to carry one or more sealing rings with sealing features, such as sealing brushes and/or labyrinth fins.
  • at plurality of sealing rings 13 are adjacently mounted in series in a turbine axial direction 28, preferably moveably mounted, on the gland carrier 12, between the turbine casing component 14 and the turbine rotor 10.
  • Each of the sealing rings 13 are adjacently located in a series in a turbine axial direction 28 along the turbine rotor 10 so as to provide a sealing means between a steam side 24 and an air side 20 of the sealing arrangement.
  • gland carriers 12 are configured in such a way that a chamber 26 is formed in the gland carrier 12 that faces the turbine casing component 14.
  • the chamber 26 is configured to eject a mixture of steam/air of else injection steam at a controlled pressure.
  • At least one chamber 26 includes a heat shield 16 covering the or each of the chambers 26 so as to partition the chamber 26 from the turbine casing component 14.
  • the purpose of the heat shield 16 is to partition the chamber 26 in such a way that there is minimise contact of steam or steam/air flowing through the or each chamber 26 thereby minimising thermal energy transfer to the turbine casing component 14. This may be achieved by the heat shield 16 extending across the chamber 26 in an essentially turbine axial direction 28.
  • the heat shield 16 is most suitable made from a material that can reduce thermal exposure and is resistant to corrosion.
  • the heat shield 16 is made stainless steel.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A steam turbine gland seal arrangement for preventing leakage of steam from around a turbine rotor (10), the gland seal arrangement comprising a chamber (26) formed in a gland carrier (12) attached to a casing component (14) and a heat shield that partitions the chamber (26) from the component (14).

Description

    TECHNICAL FIELD
  • The present disclosure relates generally to steam turbines and more particularly to multi pressure steam turbine gland arrangements of a labyrinth type for reducing steam leakage between rotating and stationary components of a steam turbine.
    • BACKGROUND INFORMATION
  • In a steam turbine, the leakage of the turbine driving steam to the outside is typically prevented by a gland sealing system. The system typically comprises a series of at least three labyrinth packing segments located along the turbine rotor in the region where the rotor exits the turbine casing. A gland carrier casing supporting the sealing rings may form at least two chambers with the turbine casing The chamber(s) enables the ejection of a mixture of steam- air and an injection of steam, when there is more than one chamber in the upstream higher pressure chamber. Each of these chambers are separated by sealing rings or labyrinth packing segments..
  • As system with not less than two chambers may, for example, comprise a first chamber in which a mixture of steam/air is injected and a second chamber with in which steam is either injected or ejected depending on the operating mode. As an example, the first chamber could operate at a pressure about 0.95 bar while the second chamber could operate at a pressure about 1.15 bar.
  • In a typically arrangement, each of the packing segments is mounted on a gland carrier casing of the turbine. In the case where the gland carrier casing component on which the sealing rings are mounted additionally forms part of the steam turbine exhaust, the turbine casing component may be exposed to local gland chambers temperature as well as steam turbine exhaust temperature. In the case of a high and intermediate pressure steam turbine having a high pressure shaft end gland system and an intermediate pressure shaft end gland system, the temperature gradient may be 110°C on the high pressure side and 70 °C on the intermediate pressure side. This may result in the turbine casing component being exposed to large thermal stresses.
    • SUMMARY
  • A steam turbine gland seal arrangement is disclosed that can provide a means of reducing thermal stresses in turbine casing components on which seal segments are mounted thereby improving, for example, the tightness of the typical horizontal joint plane at which upper and lower parts of a typical steam turbine casing are jointed together by reducing thermal stresses in the extremity of the casing due to steam temperature differences between the turbine exhaust and the gland exhaust chamber..
  • It attempts to address this problem by means of the subject matter of the independent claim. Advantageous embodiments are given in the dependent claims.
  • The disclosure is based on the general idea of providing a heat shield in chambers formed between and by gland carrier and a turbine casing component. The heat shields are arranged such that direct contact of the turbine casing component and steam flow in the chambers is avoided. In this way, a space between thermal shields and inner surface of the casing is created. This spaces acts as insulation thus avoiding a local cooling of the horizontal upper and lower half jointing flange, thus reducing joint distortion which in turn has the possible effect of improving joint tightness,
  • An aspect provides a steam turbine gland seal arrangement for preventing leakage of steam from around a turbine rotor. The gland seal arrangement comprises a turbine casing component configured to be a portion of a steam turbine exhaust, a gland carrier and a plurality of sealing segment adjacently mounted in series on the gland carrier in a turbine axial direction, for sealing along a turbine axial direction of the rotor.
  • The casing component and the gland carrier are configured and arranged such that at least two chambers are formed, wherein the chamber includes a heat shield extending to partition the chamber.
  • In an aspect, the heat shield is bolted to the gland carrier.
  • In another aspect, the heat shield is made of stainless steel.
  • Other aspects and advantages of the present disclosure will become apparent from the following description, taken in connection with the accompanying drawing, which by way of example, illustrates an exemplary embodiment of the present invention.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • By way of example, an embodiment of the present disclosure is described more fully hereinafter with reference to the accompanying drawing, in which:
    • Figure 1 is a cross sectional view of a steam turbine gland seal according to a preferred embodiment of the disclosure.
    DETAILED DESCRIPTION
  • An exemplary embodiment of the present disclosure is now described with references to the drawing, wherein like reference numerals are used to refer to like elements throughout. In the following description, for purposes of explanation, numerous specific details are set forth to provide a thorough understanding of the disclosure. However, the present disclosure may be practiced without these specific details, and is not limited to the exemplary embodiment disclosed herein.
  • An exemplary steam turbine gland seal arrangement shown in Fig. 1 is mounted around a turbine rotor 10. The gland seal arrangement includes a turbine casing component 14, a gland carrier 12 mounted on the turbine casing component 14, a chamber formed by the turbine casing component 14, the gland carrier 12, and a heat shield 16 formed between the turbine casing component 14 and the gland carrier 12.
  • The turbine casing component 14 may be configured as a portion of a steam turbine exhaust 22. That is, the turbine casing component 14 may be configured to be partially located in a flow path region of the steam turbine downstream of turbine blades where steam is expanded. While in one exemplary embodiment, the turbine casing component 14 is made of a single piece, in another exemplary embodiment, the turbine casing component 14 is made of several pieces that are bonded, joined or welded in a way that enables thermal conduction through the turbine casing component 14.
  • In an exemplary embodiment shown in Fig. 1 a gland carrier 12 is a sealing carrying member whose purpose is to carry one or more sealing rings with sealing features, such as sealing brushes and/or labyrinth fins. As shown in Fig. 1, in an exemplary embodiment, at plurality of sealing rings 13 are adjacently mounted in series in a turbine axial direction 28, preferably moveably mounted, on the gland carrier 12, between the turbine casing component 14 and the turbine rotor 10. Each of the sealing rings 13 are adjacently located in a series in a turbine axial direction 28 along the turbine rotor 10 so as to provide a sealing means between a steam side 24 and an air side 20 of the sealing arrangement.
  • As shown in Fig. 1, in an exemplary embodiment, gland carriers 12 are configured in such a way that a chamber 26 is formed in the gland carrier 12 that faces the turbine casing component 14. In an exemplary embodiment, the chamber 26 is configured to eject a mixture of steam/air of else injection steam at a controlled pressure.
  • In an exemplary embodiment shown in Fig. 1, at least one chamber 26 includes a heat shield 16 covering the or each of the chambers 26 so as to partition the chamber 26 from the turbine casing component 14. The purpose of the heat shield 16 is to partition the chamber 26 in such a way that there is minimise contact of steam or steam/air flowing through the or each chamber 26 thereby minimising thermal energy transfer to the turbine casing component 14. This may be achieved by the heat shield 16 extending across the chamber 26 in an essentially turbine axial direction 28.
  • . The heat shield 16 is most suitable made from a material that can reduce thermal exposure and is resistant to corrosion. In an exemplary embodiment the heat shield 16 is made stainless steel.
  • Although the disclosure has been herein shown and described in what is conceived to be the most practical exemplary embodiment, it can be embodied in other specific forms. The presently disclosed embodiment is therefore considered in all respects to be illustrative and not restricted. The scope of the disclosure is indicated by the appended claims rather that the foregoing description and all changes that come within the meaning and range and equivalences thereof are intended to be embraced therein.
    • REFERENCE NUMBERS
    • 10
    Rotor
    12
    Gland carrier
    13
    Sealing ring
    14
    Turbine casing component
    16
    Heat shield
    18
    Bolts
    20
    Air side
    22
    Turbine exhaust
    24
    Steam side
    26
    Chamber
    28
    Turbine axial direction

Claims (6)

  1. A steam turbine gland seal arrangement for preventing leakage of steam from around a turbine rotor (10), the gland seal arrangement comprising:
    a turbine casing component (14) configured to be a portion of a steam turbine exhaust;
    a gland carrier (12) mounted on the turbine casing component (14) have a plurality of sealing rings (13) arranged in series in a turbine axial direction (28) for sealing along a turbine axial direction (28) of the turbine rotor (10); and
    at least two chambers (26) formed in the gland carrier (12) facing the turbine casing component (14),
    characterised by a heat shield (16) arranged to covering the chamber (26) so as to partition the chamber (26) from the turbine casing (14).
  2. The steam turbine gland seal arrangement of claim 1 wherein the heat shield (16) extends essential in a turbine axial direction (28).
  3. The steam turbine gland seal arrangement of claim 1 wherein the heat shield (16) comprises bolts (18) configured and arranged to attach the heat shield (16) to the gland carrier (12).
  4. The steam turbine gland seal arrangement of claim 1 wherein the heat shield (16) is made of stainless steel.
  5. The steam turbine gland seal arrangement of claim 1 comprising three chambers (26) wherein each chamber (26) includes the heat shield (16).
  6. The steam turbine gland seal arrangement of any one of claims 1 to 5 wherein the turbine casing component (14) and the gland carrier (12) form part of a steam turbine exhaust (22).
EP14290311.1A 2014-10-14 2014-10-14 Steam turbine rotor seal arrangement Active EP3009610B1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP14290311.1A EP3009610B1 (en) 2014-10-14 2014-10-14 Steam turbine rotor seal arrangement
RU2015142774A RU2679953C2 (en) 2014-10-14 2015-10-07 Steam turbine gland arrangement
US14/876,857 US9915160B2 (en) 2014-10-14 2015-10-07 Steam turbine gland arrangement
CN201510659945.9A CN105507956B (en) 2014-10-14 2015-10-14 Steam Turbine Sealing Boot Assembly

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14290311.1A EP3009610B1 (en) 2014-10-14 2014-10-14 Steam turbine rotor seal arrangement

Publications (2)

Publication Number Publication Date
EP3009610A1 true EP3009610A1 (en) 2016-04-20
EP3009610B1 EP3009610B1 (en) 2020-11-25

Family

ID=53886788

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14290311.1A Active EP3009610B1 (en) 2014-10-14 2014-10-14 Steam turbine rotor seal arrangement

Country Status (4)

Country Link
US (1) US9915160B2 (en)
EP (1) EP3009610B1 (en)
CN (1) CN105507956B (en)
RU (1) RU2679953C2 (en)

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Publication number Priority date Publication date Assignee Title
CN109630270A (en) * 2018-12-14 2019-04-16 中国航发沈阳发动机研究所 Aero-engine gas mixture thermal protection structure

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109630270A (en) * 2018-12-14 2019-04-16 中国航发沈阳发动机研究所 Aero-engine gas mixture thermal protection structure
CN109630270B (en) * 2018-12-14 2021-03-30 中国航发沈阳发动机研究所 Oil-gas mixture thermal protection structure for aircraft engine

Also Published As

Publication number Publication date
RU2015142774A3 (en) 2018-12-10
CN105507956A (en) 2016-04-20
US9915160B2 (en) 2018-03-13
US20160102569A1 (en) 2016-04-14
RU2679953C2 (en) 2019-02-14
CN105507956B (en) 2019-10-25
RU2015142774A (en) 2017-04-10
EP3009610B1 (en) 2020-11-25

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